摘要
研究了直升机在低速飞行时的鲁棒飞行控制器设计以及直升机飞行控制系统的仿真验证问题。以ADS-33D水平1操纵品质要求为设计目标，通过选择适当的加权函数矩阵，采用基于线性不矩阵等式(LMI)的H(控制器设计方法，设计了UH-60A直升机在低速飞行时的鲁棒控制器。仿真结果表明，所设计的直升机飞行控制系统具有鲁棒性，达到了给定的ADS-33D水平1操纵品质要求。
The robust controller design of a helicopter at low-speed flight and the simulation of the flight control system are investigated. The design criteria used in this study are based on a representative subset of the low-speed requirements of the Military Handling Qualities Specification ADS-33D. A robust flight controller for UH-60A helicopter is designed by using linear matrix inequality (LMI) based H( controller design method. The simulation and computation results show that the designed helicopter flight control system has stability and performance robustness, and meets given ADS-33D level 1 handling qualities requirements.
出处
《系统仿真学报》
CAS
CSCD
2001年第5期576-578,共3页
Journal of System Simulation
